CN1844839B - Integral impacting type composite canister cover - Google Patents
Integral impacting type composite canister cover Download PDFInfo
- Publication number
- CN1844839B CN1844839B CN200610040052A CN200610040052A CN1844839B CN 1844839 B CN1844839 B CN 1844839B CN 200610040052 A CN200610040052 A CN 200610040052A CN 200610040052 A CN200610040052 A CN 200610040052A CN 1844839 B CN1844839 B CN 1844839B
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- CN
- China
- Prior art keywords
- film cover
- main body
- cloth
- cover
- integral
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 239000002131 composite material Substances 0.000 title claims abstract description 18
- 230000003116 impacting effect Effects 0.000 title claims description 13
- 239000004744 fabric Substances 0.000 claims abstract description 33
- 238000000034 method Methods 0.000 claims abstract description 12
- 239000003822 epoxy resin Substances 0.000 claims abstract description 6
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 6
- 239000011521 glass Substances 0.000 claims description 10
- 239000005030 aluminium foil Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 5
- 238000004026 adhesive bonding Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 abstract description 7
- 239000003365 glass fiber Substances 0.000 abstract description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract 1
- 229910052782 aluminium Inorganic materials 0.000 abstract 1
- 239000011888 foil Substances 0.000 abstract 1
- 239000002994 raw material Substances 0.000 abstract 1
- 239000003292 glue Substances 0.000 description 12
- 238000012360 testing method Methods 0.000 description 5
- 229920000742 Cotton Polymers 0.000 description 4
- 238000007373 indentation Methods 0.000 description 4
- 238000000465 moulding Methods 0.000 description 4
- 239000004033 plastic Substances 0.000 description 4
- 229920003023 plastic Polymers 0.000 description 4
- 229920006267 polyester film Polymers 0.000 description 4
- 229920005989 resin Polymers 0.000 description 4
- 239000011347 resin Substances 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 238000009941 weaving Methods 0.000 description 3
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 2
- 239000002390 adhesive tape Substances 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000004519 grease Substances 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000013036 cure process Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000013100 final test Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/077—Doors or covers for launching tubes
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
Abstract
The invention relates to an integrated impact composite film cover, belonging to the missile emit technique. Wherein, said film cover uses glass fiber and epoxy resin as main raw materials, while the inner surface is adhered with aluminum foil as the electromagnetic shield layer; it is characterized in that: form outer to inner, it comprises a frame (1), a weal section (2), and main body (3), while the main body (3) is layered by the method that [(0degree90degree)(+- 45degree)(0degree90degree)(+-45degree)] with isotropy plates, to form the same periphery strength, and it is adhered to the frame (1); the adhering part is the weak section (2); the upper and lower surface of said adhering part are adhered with cloth or cloth bar to strengthen the weak section (2). The invention can adjust the strength of weak section via adjusting the layer number and width, to meet the demand of different pressures. The invention has simple structure and simple process.
Description
Technical field
The present invention relates to a kind of integral impacting type composite canister cover, belong to the MISSILE LAUNCHING technical field.
Background technology
The design of MISSILE LAUNCHING lid is to influence guided missile to reflect one of key factor of ability fast.Therefore, when development missile storing firing box, the design of case lid is extremely important.Major requirement is to bear certain pressure reduction, and good seal performance is opened rapidly when launching a guided missile.For satisfying above-mentioned requirements, the normal in the past mechanical cap that adopts of MISSILE LAUNCHING case lid, blasting bolt unlatching lid etc., referring to US Pat.3970006,1976, US Pat.4333381,1982, but the shortcoming of the equal various degrees of these case lids is opened lid as machinery and need be opened with hydraulic system, mechanism's complexity, not only increased the weight of case and delayed the operating time, the reaction of blast lid is opened rapidly than mechanical cap, but shoots and keep in repair more complicated again, and adopt the priming system transportation, store difficulty.
Developed the frangible membrane will lid abroad, referring to U.S. Pat Pat.4498368,1985, this kind film cover is the basic composition material with glass fibre and epoxy resin, on the layer of difference shop, scribe tear line and form weak area, film cover can be born certain well-distributed pressure and just can be made film cover with the projected path fragmentation under less concentrated force, is swift in response, and has improved MISSILE LAUNCHING efficient.But this kind composite material film is stamped its unconquerable weak point, and promptly film cover must be destroyed under the effect of guided missile end, and film cover will inevitably have a negative impact to the guided missile termination of contact film cover; J.H.WU, T.Y.Kam etc. develop the composite material film lid of another kind of version.Referring to J.H.Wu, W.T.Wang, T.Y.Kam Failure analysis of a frangible laminated compositecanister cover.Proc Inst Mech Eng, 1999, vol.213, Part G:187-95; T.Y.Kam, J.H.Wu, W.T.Wang External failure pressure of a frangible laminated compositecanister cover.Composite Structure.1999, vol.47:563-569.As shown in Figure 1, the gas shock film cover of utilizing the preceding guided missile engine of emission to produce, film cover flies with predetermined pintongs form integral body, can not have a negative impact to MISSILE LAUNCHING.As shown in Figure 2, its film cover is projection from inside to outside, and main body and framework adopt resin to glued joint and form, and main part then forms overall structure by four symmetrical plates splicing.Glued joint thickness by increasing, reduce the glue-line stress level to reach the pressure-bearing index.This kind film cover complex structure, main body and framework adopt pure resin to glued joint, and bearing capacity is less, and the weak area that adopts pure resin to connect is made difficulty, complex process.Unavoidably bring bubble into resin region in the forming process, weak area easily forms internal flaw, causes bulk strength to descend, and quality of stability is not being met.The film cover external and internal compositions is asymmetric, and inside and outside bearing capacity is inconsistent, and therefore, such film cover practical application has certain limitation.
Summary of the invention
The object of the present invention is to provide integral impacting type composite canister cover simple in structure, that bearing capacity is strong.
A kind of integral impacting type composite canister cover, with glass fabric and epoxy resin is material of main part, its inner surface is pasted with aluminium foil as screen layer, is used for preventing electromagnetic interference, it is characterized in that: this film cover inwardly comprises framework, weak area, main body by the periphery; Main body adopts the laying method of [(0 ° 90 °) (± 45 °) (0 ° 90 °) (± 45 °)] quasi-isotropic laminate, and is basic identical to guarantee film cover periphery intensity; Main body is connected with framework by glueing joint, and weld is weak area; The weld top and bottom of main body and framework also have been pasted with whole cloth or the cloth that increases the effect of weak area intensity.
The integral impacting type composite canister cover that this use is novel, have simple in structure, manufacture craft characteristic of simple. and experimental results show that, this film cover is destroyed so that desired trajectory is whole, destroying the back stays without any residue, therefore, film cover can not produce any adverse effect to the emission of guided missile, and is swift in response. in addition, can regulate weak area intensity by the number of plies, the width of regulating whole cloth or cloth, to satisfy the requirement of different pressures index.
Description of drawings
Fig. 1 is the film cover failure mode figure of external development.
Fig. 2 is the film cover version schematic diagram of external development.
Fig. 3 is an integral impacting type composite canister cover structural representation of the present invention.
Fig. 4 is an integral impacting type composite canister cover mould vertical view of the present invention.
Fig. 5 is an integral impacting type composite canister cover mould side view of the present invention.
Fig. 6 is that integral impacting type composite canister cover of the present invention breaks through the experimental rig schematic diagram.
Fig. 7 integral impacting type composite canister cover weak area of the present invention version figure.
Label title among Fig. 3: 1, framework, 2, weak area, 3, main body.
Label title among Fig. 4: 4, molding handrail.
Label title among Fig. 5: 5, patrix, 6, counterdie, 7, film cover, 8, prefabricated indentation.
Label title among Fig. 6: 9, Pressure gauge, 10, the flange circle, 11, air pump.
Label title among Fig. 7: 12, patch layer.
The specific embodiment
According to shown in Figure 3, a kind of integral impacting type composite canister cover of the present invention, with glass fabric and epoxy resin is material of main part, its inner surface is pasted with aluminium foil as screen layer, be used for preventing electromagnetic interference, it is characterized in that: film cover inwardly comprises framework 1, weak area 2, main body 3 by the periphery; Main body 3 adopts the laying method of [(0 ° 90 °) (± 45 °) (0 ° 90 °) (± 45 °)] quasi-isotropic laminate, and is basic identical to guarantee film cover periphery intensity; Main body 3 is connected with framework 1 by glueing joint, and weld is weak area 2; Main body 3 also has been pasted with whole cloth or the cloth that increases weak area 2 intensity effects with the weld top and bottom of framework 1.
Present embodiment is the manufacturing process of a film cover.Hand paste+die press technology for forming is adopted in the film cover moulding, makes through finishing film cover behind three forming and hardenings.According to design, mould adopts upper and lower modular form, and mould is shown in Fig. 4,5, and wherein the counterdie one side has the projection that prefabricated indentation is used in its border, and another side is a smooth plates.
Film cover version
1, film cover main body and framework
Be composited by several layers 0.2 plain woven glass cloth and epoxy resin, the shop layer is [(0 ° 90 °) (± 45 °) (0 ° 90 °) (± 45 °)] quasi-isotropic symmetrical structure;
2, weak area version
Directly glueing joint between main body and framework, is a circle glue-line, and upper and lower surface is respectively pasted 1-3 layer 0.1 plain woven glass cloth, and weak area version is (upper and lower surface is respectively pasted the layer glass cloth) as shown in Figure 7.
The film cover manufacture craft
Film cover is made by finishing film cover behind three forming and hardenings and is made.
1, film cover one-step solidification technology
1) counterdie and the cope match-plate pattern of projection worn in cleaning one;
2) on counterdie, smear the low temperature grease, shear the polyester film plastic paper, and be attached on the counterdie according to the counterdie shape;
3) prepare glue on request;
4) shearing 0.2 plain weaving machine on request in advance weaves cotton cloth;
5) ground floor cloth is layered on the counterdie and has scraped glue along 0 ° of 90 ° of direction, ground floor is cut off along the counterdie indentation;
6) second layer cloth is layered on the counterdie and has scraped glue along ± 45 ° of direction, the second layer is cut off along the counterdie indentation;
7) lay the woven glass cloth of specifying the number of plies according to [(0 ° 90 °) (± 45 °) (0 ° 90 °) (± 45 °)] order successively, and scraped glue;
8) cover polyester film, unnecessary glue and bubble are scraped with the plastics scraper;
9) upper mould cover is being completed on the counterdie of cloth, and weighting material compresses.
10) treat to carry out the demoulding after 24 hours film cover are solidified.
2, regelate moulding process
1) adopts the counterdie another side as the mould lower surface, cleared up counterdie and cope match-plate pattern;
2) on counterdie, smear the low temperature grease, and shear the polyester film plastic paper according to the counterdie shape;
3) on counterdie, spread aluminium foil and prune by the profile of counterdie, with the cotton yarn that speckles with acetone that the cleaning oil pollution on the aluminium foil is clean, and finish cross hairs to determine the direction of shop, back fiber cloth;
4) prepare glue on request;
5) shearing 0.1 plain weaving machine on request in advance weaves cotton cloth;
6) will carve to stitch with adhesive tape and seal along carving the seam direction in the one side of film cover;
7) ground floor cloth is layered on the film cover another side that stitches prefabricated quarter along 0 ° of 90 ° of direction, has scraped glue, will specify the cloth of the number of plies to spread again successively along 0 ° of 90 ° of direction;
8) along carving seam glass cloth is opened quarter, carved open position from carving seam 10-20mm;
9) brush glue posting on the counterdie of aluminium foil then, will complete a cover of cloth on counterdie;
10) upper mould cover is being completed on the counterdie of cloth, and weighting material compresses
11) treat to carry out the demoulding after 24 hours film cover are solidified.
3, three cure process
1) adhesive tape in the post forming process is torn after, will carve seam and add full with glue;
2) shearing 0.1 plain weaving machine on request in advance weaves cotton cloth;
3) ground floor cloth is layered on the film cover along 0 ° of 90 ° of direction, has scraped glue, will specify 0.1 plain weave glass cloth of the number of plies to spread again, and scrape glue;
4) along carving seam glass cloth is opened quarter, carved open position from carving seam 10-20mm;
5) cover polyester film, unnecessary glue and bubble are scraped with the plastics scraper;
6) upper mould cover is being completed on the counterdie of cloth, and weighting material compresses;
7) treat to carry out the demoulding after 24 hours film cover are solidified.
Film cover behind three curing moldings is positioned in the baking oven, is post processing 3 hours in 50 ℃ the environment in temperature, takes out after cooling.
Embodiment 2
Present embodiment, be that a film cover is broken through the test detailed process. experimental rig is as shown in Figure 6. on request film cover is contained on the test tube, open air compressor, turn off air compressor after waiting to be added to 0.8MPa pressure, open intake valve pressurising slowly and examine the film cover distortion. keep a period of time after waiting to be pressurized to certain pressure, whether the viewing film lid has the sound, whether layering is arranged, observe pressure gauge reading simultaneously whether decline is arranged in pressure maintaining period, be offloaded to 0.00MPa then, whether the viewing film lid has residual deformation, whether damage is arranged. repeat above process, distortion of viewing film lid and unloading back residual deformation situation. to be determined do not have to damage, to carry out film cover under the good situation of air-tightness and break through test. slowly pressurising examines pressure gauge reading, record test breakdown pressure, viewing film covers flight path a long way off simultaneously. and treat to take a picture after film cover is destroyed and write down the final test phenomenon, finish test.
Claims (1)
1. integral impacting type composite canister cover, with glass fabric and epoxy resin is material of main part, its inner surface is pasted with aluminium foil as screen layer, be used for preventing electromagnetic interference, it is characterized in that: this film cover inwardly comprises framework (1), weak area (2), main body (3) by the periphery; Main body (3) adopts the laying method of [(0 ° 90 °) (± 45 °) (0 ° 90 °) (± 45 °)] quasi-isotropic laminate, and is basic identical to guarantee film cover periphery intensity; Main body (3) is connected with framework (1) by glueing joint, and weld is weak area (2); Main body (3) also has been pasted with whole cloth or the cloth that increases weak area (2) intensity effect with the weld top and bottom of framework (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610040052A CN1844839B (en) | 2006-04-30 | 2006-04-30 | Integral impacting type composite canister cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610040052A CN1844839B (en) | 2006-04-30 | 2006-04-30 | Integral impacting type composite canister cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1844839A CN1844839A (en) | 2006-10-11 |
| CN1844839B true CN1844839B (en) | 2010-05-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200610040052A Expired - Fee Related CN1844839B (en) | 2006-04-30 | 2006-04-30 | Integral impacting type composite canister cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1844839B (en) |
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| CN103542773B (en) * | 2013-11-04 | 2015-04-01 | 上海燕兴科技实业有限公司 | Fragile rear cover of launching cylinder of weapon system |
| CN103542769B (en) * | 2013-11-04 | 2015-09-30 | 上海燕兴科技实业有限公司 | A kind of manufacture method of breakable launcher back cover of weapon system |
| CN103913098A (en) * | 2014-03-12 | 2014-07-09 | 南京航空航天大学 | Multi-petal composite material launching box cover and preparation method thereof |
| CN104237022A (en) * | 2014-09-17 | 2014-12-24 | 南京航空航天大学 | Two-stage series-connection type launching simulation test device for composite fragile cover and simulation method |
| CN105952890B (en) * | 2016-06-29 | 2018-01-30 | 贵州航天天马机电科技有限公司 | A kind of frangible protection cap structure of the big positive and negative pressure of frame type |
| CN106895740A (en) * | 2017-01-19 | 2017-06-27 | 上海机电工程研究所 | Composite material film protecgulum with rubber as matrix and preparation method thereof |
| CN109631669B (en) * | 2018-12-21 | 2021-03-12 | 上海燕兴科技实业有限公司 | Fragile cover of launching box of guided missile analog launching system |
| CN109703062B (en) * | 2019-01-31 | 2021-08-13 | 上海材料研究所 | Method for manufacturing emission box end cover by adopting vacuum-assisted resin diffusion molding process |
| CN110953929B (en) * | 2019-11-12 | 2022-04-08 | 南京航空航天大学 | Breakable lid of carbon-fibre composite |
| CN112985174B (en) * | 2021-02-10 | 2023-01-10 | 上海材料研究所 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
| CN115014125B (en) * | 2022-06-17 | 2023-07-04 | 北京新风航天装备有限公司 | Broken carbon fiber composite fragile film cover according to preset path |
| CN117989921A (en) * | 2024-04-03 | 2024-05-07 | 四川爱思达航天科技有限公司 | Fragile cover for differential bearing of internal and external pressure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4498368A (en) * | 1983-10-06 | 1985-02-12 | The United States Of America As Representedby The Secretary Of The Navy | Frangible fly through diaphragm for missile launch canister |
| CN1419101A (en) * | 2002-12-19 | 2003-05-21 | 上海交通大学 | Composite material made box body structure for storage and conveying launch box |
| CN200962016Y (en) * | 2006-04-30 | 2007-10-17 | 南京航空航天大学 | Whole impact breaking compound material film cover |
-
2006
- 2006-04-30 CN CN200610040052A patent/CN1844839B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4498368A (en) * | 1983-10-06 | 1985-02-12 | The United States Of America As Representedby The Secretary Of The Navy | Frangible fly through diaphragm for missile launch canister |
| CN1419101A (en) * | 2002-12-19 | 2003-05-21 | 上海交通大学 | Composite material made box body structure for storage and conveying launch box |
| CN200962016Y (en) * | 2006-04-30 | 2007-10-17 | 南京航空航天大学 | Whole impact breaking compound material film cover |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1844839A (en) | 2006-10-11 |
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